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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society of Propulsion Engineers
Journal Basic Information
Journal DOI :
The Korean Society of Propulsion Engineers
Editor in Chief :
Volume & Issues
Volume 19, Issue 6 - Dec 2015
Volume 19, Issue 5 - Oct 2015
Volume 19, Issue 4 - Aug 2015
Volume 19, Issue 3 - Jun 2015
Volume 19, Issue 2 - Apr 2015
Volume 19, Issue 1 - Feb 2015
Selecting the target year
An Experimental Study on Flow Characteristics of Cavitation Venturi
Yoon, Wonjae ; Ahn, Kyubok ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 1~7
DOI : 10.6108/KSPE.2015.19.4.001
A cavitation venturi is a device that allows a liquid flow rate to be fixed or locked independent of a downstream pressure and has been successfully used in a liquid rocket engine system which requires a stable propellant flow rate. In the present research, four cavitation venturis which have same dimensions except for converging inlet angle and diverging outlet angle, were designed and manufactured. Flow rates through each venturi and upstream/downstream pressures were measured by changing the pressures. From the experimental data, the discharge coefficients and critical pressure ratios were calculated for each venturi. It was found that the inlet and outlet angles of the cavitation venturi affected the discharge coefficient, and the outlet angle influenced on the critical pressure ratio.
Spray Characteristics of Closed-type Swirl Injectors with Varying Swirl Chamber Geometry
Chung, Yunjae ; Jeong, Seokkyu ; Oh, Sukil ; Yoon, Youngbin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 8~14
DOI : 10.6108/KSPE.2015.19.4.008
This study has been done as a preliminary work in the process of confirming the modeling and calculation results on the dynamic characteristics of closed-type swirl injector which were performed by Ismailov et al. in Purdue university. Closed-type swirl injectors with replaceable swirl chamber parts were designed and manufactured. The steady state spray characteristics of closed-type swirl injector with varying swirl chamber length and diameter were verified. Mass flow rate was measured with a mass flow meter installed in front of the injector, and liquid film thickness was measured by Lefebvre`s method with electrodes installed at the orifice of the injector. Variation of spray cone angle and break-up length were investigated from the spray images captured under different manifold pressure conditions.
Effects of Acoustic Boundary Conditions on Combustion Instabilities in a Gas Turbine Combustor
Lim, Jaeyoung ; Kim, Deasik ; Kim, Seong-Ku ; Cha, Dong Jin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 15~23
DOI : 10.6108/KSPE.2015.19.4.015
This study predicts the basic characteristics of combustion instabilities in a gas turbine lean premixed combustor using ASCI3D code which is a FEM(Finite Element Method)-based Helmholtz solver. The prediction results show the good agreement with the measured data in modeling the overall combustion instability features, however, the code is found to overpredict the unstable conditions. As one of the efforts to improve the model accuracy, the effects of acoustic boundary conditions on the instability growth rate are analyzed. As a result, it is shown that the acoustic reflection coefficient has a great impact on the instability and the prediction accuracy can be enhanced by defining the precise acoustic conditions.
A Prediction of Infrared Spectrum of Rocket Plume with Considering Soot Particles
Jo, Sung Min ; Nam, Hyun Jae ; Kim, Duk Hyun ; Kwon, Oh Joon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 24~36
DOI : 10.6108/KSPE.2015.19.4.024
In the present study, numerical predictions of infrared spectrum of rocket plume with considering effect of particles based on approximation theories were performed by using a line-by-line radiation model with radiation databases. The high-resolution radiation databases were used to predict thermal emission spectra of gas molecules within the rocket plume regime. The particles were modeled as soot particles by using 1st term approximation of Mie theory and Rayleigh approximation. The reliability of modeled effect of soot particles using the two approximation theories was verified, and the spectral radiance of rocket plume was predicted based on the verification. The results were improved in the short wavelength range by considering the effect of soot particles.
Frequency-Equivalence Ratio Correlation Analysis of Methane-Air Premixed Flame Influenced by Ultrasonic Standing Wave (I)
Kim, Min Sung ; Kim, Jeong Soo ; Koo, Jaye ; Kwon, Oh Chae ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 37~44
DOI : 10.6108/KSPE.2015.19.4.037
An experimental study was performed for the analysis of frequency-equivalence ratio correlation in the methane-air premixed flame influenced by ultrasonic standing wave. Evolutionary features of the propagating flame were caught by high-speed camera, and the variation of flame-behavior including local velocities was investigated in detail using a post-processing analysis of the high-speed images. It was found that propagation-velocity augmentation of the methane-air premixed flame by the intervention of ultrasonic standing wave was made in leaner mixture, but the velocity diminished when the strength of chemical reaction was saturated around the slightly fuel-rich side of stoichiometry.
Frequency-Equivalence Ratio Correlation Analysis of Methane-Air Premixed Flame Influenced by Ultrasonic Standing Wave (II)
Kim, Min Sung ; Bae, Dae Seok ; Kim, Jeong Soo ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 45~51
DOI : 10.6108/KSPE.2015.19.4.045
An experimental study was performed for the analysis of frequency-equivalence ratio correlation in the methane-air premixed flame influenced by ultrasonic standing wave. The propagating flame was caught by high-speed Schlieren photography, and the variation of flame-behavior including the flame structure was investigated in detail employing a post-processing analysis of the high-speed images. It was found that a structural variation and propagation-velocity augmentation of the methane-air premixed flame by the intervention of ultrasonic standing wave were more caused off around the stoichiometry. Also, a dependency of the flame behaviors on the driving frequency and equivalence ratio of the reactants was confirmed.
Design of Gun Launched Ramjet Propelled Artillery Shell with Inviscid Flow Assumption
Kang, Shinjae ; Park, Chul ; Jung, Woosuk ; Kwon, Taesoo ; Park, Juhyeon ; Kwon, Sejin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 52~60
DOI : 10.6108/KSPE.2015.19.4.052
Operation area of corps was expanded under military reformation, and extending range of 155 mm howitzer became important issue. New approach is needed to extend range to 80 kim. Ramjet engine is air breathing engine, and it can provide specific impulse several times more than solid rocket motor so that range is extended using same weight of propellant. If the ramjet engine is gun-launched system, it does not require any other booster because muzzle velocity is near Mach 3. Especially solid fuel ramjet (SFRJ) does not have any moving part so that it is favorable for gun-launching system which is under high stress during launching. In this paper, we design air intake, combustion chamber, and nozzle of 155 mm gun launched ramjet propelled artillery shell with inviscid flow assumption. We conduct parameter study to have range more than 80 km, and maximum high explosive volume.
Comparison between GOx/Kerosene and GN
O/Ethanol Reactive Spray in a Subscale Liquid Rocket Engine
Choi, Songyi ; Shin, Bongchul ; Lee, Keonwoong ; Kim, Dohun ; Koo, Jaye ; Park, Dong-Kun ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 61~68
DOI : 10.6108/KSPE.2015.19.4.061
Reactive sprays of two propellant combinations(GOx/kerosene and
/ethanol) were observed and compared with each other as a basic research of visualizing supercritical combustion. A shadowgraph imaging method was used to visualize the reactive sprays, and shadowgraph images were converted to density gradient magnitude images to analyse the structure of reactive sprays. The gas-liquid interface of GOx/kerosene spray showed rougher boundary and steeper density gradient near the injector face than the
/ethanol at similar combustion chamber pressure. Spray core length was calculated from averaged density gradient magnitude images and it was revealed that spray core length of GOx/kerosene was shorter than that of
/ethanol, although momentum flux ratio of GOx/kerosene propellant combination was lower.
Synthesis and Crystallization of Hydrazinium Nitroformate(HNF) as Eco-friendly Oxidizer
Kim, Jina ; Kim, Min Jun ; Min, Byoung Sun ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 69~76
DOI : 10.6108/KSPE.2015.19.4.069
Recently, environmental sustainability of the transitional explosives and propellants is an issue of growing importance in energetic materials. For examples, ammonium perchlorate(AP) as an solid propellants oxidizer could create a poisonous gas and atmospheric pollutions, such as HCl. Among the several oxidizers, hydrazinium nitroformate(HNF) is an effective candidate substance for eco-friendly oxidizer, which has high density, pressure index, and less smog generating property during combustion for the Divert and Attitude Control System(DACS). This study was confirmed a synthesis through various conditions, was performed for the essential data of solubility the crystallization process. Also, crystallization process such as cooling, drowning-out and sonication were performed.
A Research for Energy Harvest/Distribution/Control of HALE UAV based on the Solar Energy
Nam, Yoonkwang ; Park, To Soon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 77~84
DOI : 10.6108/KSPE.2015.19.4.077
Recently, as the needs for eco-friendly aero propulsion system increase gradually, many study works have been conducted to develop the hybrid propulsion system for High Altitude Long Endurance(HALE) UAV. In this study, we analyzed both suitable energy distribution and management methodology among the total energy collected from solar cell and the total required energy of aerial vehicle and required energy of the regenerative fuel cell(RFC) for driving in the night time and optimized the energy balance mechanism based on the ascribed mission profile.
Construction and Validation Test of Turbopump Real-propellant Test Facility
Kim, Jin-Sun ; Han, Yeoung-Min ; Ko, Youngsung ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 85~93
DOI : 10.6108/KSPE.2015.19.4.085
Liquid rocket engines of KSLV-II employ a turbopump feed system for propellants. A turbopump real-propellant test facility based on liquid oxygen and kerosene has been constructed for the experimental verification of the turbopump performance using the real media of propellants(i.e., LOX/Kerosene). The verification tests of sub-systems were performed such as LOX/kerosene feed system and alcohol burner system. Finally, the performance of the whole system was executed and verified through a sets of validation tests with the development model of the KSLV-II turbopumps. It has been confirmed that the test facility satisfies the operating conditions and time of the turbopump at the design and off-design performance test using real-propellant.
Configuration and Ground Tests of Solar Cell and Fuel Cell Powered System for Long Endurance UAV
Park, Byeongseob ; Kim, Hyuntak ; Baek, Seungkwan ; Kwon, Sejin ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 94~101
DOI : 10.6108/KSPE.2015.19.4.094
Each of power systems of solar cell and fuel cell were configured and validated for long endurance UAV, as the preliminary research for the integration of power systems. Solar power system consisted of solar modules fabricated by solar cells of Sunpower`s C60, commercial solar MPPT controller and Li-po battery, and then was validated. The re-start characteristics of hydrogen production from
hydrolysis was validated for operating the commercial fuel cell. The average voltage drop of Li-po battery in solar power system was -2.9 V/hour. The performance of re-start characteristics of
hydrolysis was stable in sequence mode of mission profile. Each of single systems were satisfied for the proposed mission profile.
A Study of Loading Conditions for Developing the High-speed Bearings of the Gas-turbine Engine
Kim, Sun Je ; Kim, Yeong Ryeon ;
Journal of the Korean Society of Propulsion Engineers, volume 19, issue 4, 2015, Pages 102~109
DOI : 10.6108/KSPE.2015.19.4.102
The methodology to calculate loads on the bearings of the gas-turbine engine is presented for design of high-speed bearing. Firstly, the loads on the bearings are formulated according to the force and moment equilibrium with gyroscopic moment in three-dimensional space. Afterward, operating loading conditions of the engine are presented by applying the Joint Service Specification Guide, and magnitudes of transient and steady bearing loads are estimated based on the operating conditions. The calculated loading conditions of the bearings will be used for the essential design boundaries for the detail structural design and rig test.